Study of Passive Control in a Transonic Shock Wave/Boundary-Layer Interaction

Bur, Reynald; Corbel, Bernard; Délery, Jean

doi:10.2514/2.376

Cited by 82 publications

(9 citation statements)

References 7 publications

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“…Two-component laser Doppler velocimetry (LDV) measurements performed in the same configuration and facility (Bur, Corbel & Délery 1998;Bur, Coponet & Carpels 2009) have shown that upstream of the shock, the boundary layer on the bump is fully turbulent with a physical thickness δ = 4 mm and a momentum thickness Θ = 0.25 mm. The shock position is monitored by the evolution of static pressure through 36 pressure taps on the lower wall (see figure 12b).…”

Section: Experimental Investigationmentioning

confidence: 98%

Unsteadiness in transonic shock-wave/boundary-layer interactions: experimental investigation and global stability analysis

Sartor¹,

Mettot²,

Bur³

et al. 2015

J. Fluid Mech.

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A transonic interaction between a shock wave and a turbulent boundary layer is experimentally and theoretically investigated. The configuration is a transonic channel flow over a bump, where a shock wave causes the separation of the boundary layer in the form of a recirculating bubble downstream of the shock foot. Different experimental techniques allow for the identification of the main unsteadiness features. As recognised in similar shock-wave/boundary-layer interactions, the flow field exhibits two distinct characteristic frequencies, whose origins are still controversial: a low-frequency motion which primarily affects the shock wave; and medium-frequency perturbations localised in the shear layer. A Fourier analysis of a series of Schlieren snapshots is performed to precisely characterise the structure of the perturbations at low-and medium-frequencies. Then, the Reynolds-averaged Navier-Stokes (RANS) equations closed with a Spalart-Allmaras turbulence model are solved to obtain a mean flow, which favourably compares with the experimental results. A global stability analysis based on the linearization of the full RANS equations is then performed. The eigenvalues of the Jacobian operator are all damped, indicating that the interaction dynamic cannot be explained by the existence of unstable global modes. The input/output behaviour of the flow is then analysed by performing a singular-value decomposition of the Resolvent operator; pseudo-resonances of the flow may be identified and optimal forcings/responses determined as a function of frequency. It is found that the flow strongly amplifies both medium-frequency perturbations, generating fluctuations in the mixing layer, and low-frequency perturbations, affecting the shock wave. The structure of the optimal perturbations and the preferred frequencies agree with the experimental observations.

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Section: Experimental Investigationmentioning

confidence: 98%

Unsteadiness in transonic shock-wave/boundary-layer interactions: experimental investigation and global stability analysis

Sartor¹,

Mettot²,

Bur³

et al. 2015

J. Fluid Mech.

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“…In the present conditions the ratio between the two throat sections is 1.12, and the shock occurs at Mach = 1.4 before the end of the profile. Two-component LDV measurements 27 showed that on the bump the boundary layer is fully turbulent with a physical thickness δ = 4 mm and a momentum thickness Θ = 0.25 mm.…”

Section: Experimental Investigationmentioning

confidence: 99%

Dynamics of a shock-induced separation in a transonic flow: a linearized approach

Sartor¹,

Mettot²,

Sipp³

et al. 2013

43rd Fluid Dynamics Conference

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A transonic interaction between a shock wave and a turbulent boundary layer in a Mach 1.4 channel flow is experimentally and theoretically investigated. The configuration is a well documented transonic flow over a bump, where a strong shock wave causes the separation of the boundary layer and a recirculating bubble is observed downstream of the shock foot. As recognized in similar configurations, the flow presents two distinguished characteristic frequencies, whose origins are still unknown. In the present study we assume that the unsteadiness may be due to a frequency selection process and a theoretical approach is proposed to verify this feature. First, experimental investigations allow to characterize the unsteady behavior of the interaction. Then, a base flow solution of Reynolds-averaged Navier-Stokes equations is considered, and a linearized approach based on a singular value decomposition of the global resolvent is performed. The noise-amplifier behavior of the flow is highlighted by the linearized approach: high-frequency perturbations are shown to be the most amplified in the mixing layer, whilst the shock wave behave as a lowpass filter. The mechanisms that are responsible for these two phenomena are discussed and a comparison with unsteady pressure measurement and Fourier modes of high speed Schlieren photography is performed.

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“…In air inlets, undesirable events such as decrement in flow capture, increment in spillage drag and even unstart situation may occur during the flight. Since the 1960s, many experimental and computational studies have been performed to better understand the flow conditions in the supersonic air inlets [3][4][5][6][7][8][9][10][11]. In the present study, a series of flow visualization experiments and fluctuation surface pressure measurements were performed as an attempt to improve our knowledge and understanding of the flow within the internal compression supersonic inlets.…”

Section: Introductionmentioning

confidence: 97%

Flow Visualization and Fluctuating Pressure Measurements in an Internal Compression Inlet

Tabanli

Yuceil

2015

53rd AIAA Aerospace Sciences Meeting

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Flow visualization experiments and fluctuating pressure measurements were conducted in supersonic internal compression inlet models in a Mach 2 flow. In the first phase of the study, the inlet model consisted of a single sharp-edged shock generator on the upper lip of the inlet. In the second phase, another ramp was added to the floor at the entrance of the single-ramp inlet model in order to fully represent an internal compression inlet. A block mechanism is placed at the exit of the inlet channel to simulate the pressure condition caused by the presence of the engine. Experiments were performed to investigate the multi-shock wave flow pattern. Shadowgraph imaging method was used to obtain the shock wave structure within the inlet and surface oil flow visualization technique was used to provide diagnostic information about the flow structure on floor of the model. Fluctuating pressure measurements were also performed on the floor of the inlet model at various locations by using fast-response pressure transducers. Shock wave pattern obtained from shadowgraph results and the distribution of mean and rms pressures obtained from dynamic pressure measurements were combined to study the shock boundary layer interaction occurring in the flow over the floor of the inlet model. Results of pressure measurements and flow visualization were interpreted together to improve our understanding of the complex flow in the inlet. Nomenclature M= Mach number p∞ = freestream pressure pm = mean pressure σp = quadratic mean pressure

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Study of Passive Control in a Transonic Shock Wave/Boundary-Layer Interaction

Cited by 82 publications

References 7 publications

Unsteadiness in transonic shock-wave/boundary-layer interactions: experimental investigation and global stability analysis

Unsteadiness in transonic shock-wave/boundary-layer interactions: experimental investigation and global stability analysis

Dynamics of a shock-induced separation in a transonic flow: a linearized approach

Flow Visualization and Fluctuating Pressure Measurements in an Internal Compression Inlet

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